Development of a Liquid Rocket Ground Demonstrator Through Thermal Analyses

Ricci, Daniele; Battista, Francesco; Ferraiuolo, Michele; Natale, Pasquale; Fragiacomo, Manrico

doi:10.1080/01457632.2019.1600879

Cited by 5 publications

(6 citation statements)

References 9 publications

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“…With reference to the aforementioned Figure 4 the considered solid material for the liner part is a copper alloy (CuCrZr) while the electrodeposited layers are made up of pure copper and pure nickel. All the thermophysical properties of such materials were considered temperature-dependent and calculated through a dedicated characterization activity [14]. Results were in line with literature data, as shown in [42].…”

Section: Numerical Modelingsupporting

confidence: 70%

“…Moreover, a validated numerical procedure has been set up in view of being adopted to run the thermal simulations on the HYPROB final Demonstrator first unit (DEMO-0A), supporting the detailed design. Further information on the program and on the realized breadboards are available in [14,16,38]. It is worth highlighting that the application of the classical semiempirical correlations, adopted to calculate the evaluation of heat-transfer coefficients, does not produce reliable results in the deteriorated mode, and in addition, high values of relative roughness also represent a challenging condition from the numerical-modeling point of view.…”

Section: Transcritical Behavior Of Methane In a Lre Cooling Jacketmentioning

confidence: 99%

Section: Transcritical Behavior Of Methane In a Lre Cooling Jacketmentioning

confidence: 99%

“…Moreover, another strong point has been recently underlined since methane could be "extracted" on Mars in a view of in situ resource utilization framework, and this results into a desirable feature for ascent/descent applications in future planetary-exploration missions [12,13]. In fact, the flexibility of application makes methane an interesting solution for several missions, including access to space (from first stages of launchers to upper stages) and in-space systems (such as service modules, landing or descent vehicles, and ascent stages) [14]. Moreover, Italy is investing in the development and consolidation of methane-based space propulsion systems both on the private and public sides.…”

Section: Introductionmentioning

confidence: 99%

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Transcritical Behavior of Methane in the Cooling Jacket of a Liquid-Oxygen/Liquid-Methane Rocket-Engine Demonstrator

2022

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The successful design of a liquid rocket engine is strictly linked to the development of efficient cooling systems, able to dissipate huge thermal loads coming from the combustion in the thrust chamber. Generally, cooling architectures are based on regenerative strategies, adopting fuels as coolants; and on cooling jackets, including several narrow axial channels allocated around the thrust chambers. Moreover, since cryogenic fuels are used, as in the case of oxygen/methane-based liquid rocket engines, the refrigerant is injected in liquid phase at supercritical pressure conditions and heated by the thermal load coming from the combustion chamber, which tends to experience transcritical conditions until behaving as a supercritical vapor before exiting the cooling jacket. The comprehension of fluid behavior inside the cooling jackets of liquid-oxygen/methane rocket engines as a function of different operative conditions represents not only a current topic but a critical issue for the development of future propulsion systems. Hence, the current manuscript discusses the results concerning the cooling jacket equipping the liquid-oxygen/liquid-methane demonstrator, designed and manufactured within the scope of HYPROB-NEW Italian Project. In particular, numerical results considering the nominal operating conditions and the influence of variables, such as the inlet temperature and pressure values of refrigerant as well as mass-flow rate, are shown to discuss the fluid transcritical behavior inside the cooling channels and give indications on the numerical methodologies, supporting the design of liquid-oxygen/liquid-methane rocket-engine cooling systems. Validation has been accomplished by means of experimental results obtained through a specific test article, provided with a cooling channel, characterized by dimensions representative of HYPROB DEMO-0A regenerative combustion chamber.

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Section: Numerical Modelingsupporting

confidence: 70%

Section: Transcritical Behavior Of Methane In a Lre Cooling Jacketmentioning

confidence: 99%

Section: Transcritical Behavior Of Methane In a Lre Cooling Jacketmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Transcritical Behavior of Methane in the Cooling Jacket of a Liquid-Oxygen/Liquid-Methane Rocket-Engine Demonstrator

2022

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“…The line of development of the HYPROB Program involved the study of a series of "demonstrators", leading to designing, manufacturing, and the final testing of a 30-kN-thrust LOX/LCH 4 engine (DEMO). An incremental approach strategy was adopted using in-house designing and testing of specific breadboards, enabling the understanding of the basic physical phenomena, the critical aspects associated with methane/oxygen supercritical combustion, and the application of additive manufacturing techniques [46], as shown by Figure 1a. The first unit of DEMO, named DEMO-0A, successfully withstood a firing campaign in December 2022, allowing for the qualification of the thrust chamber, manufactured through electrodeposition (Figure 1b).…”

Section: Introductionmentioning

confidence: 99%

Thermal Behaviour of the Cooling Jacket Belonging to a Liquid Oxygen/Liquid Methane Rocket Engine Demonstrator in the Operation Box

et al. 2023

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The cooling jackets of liquid rocket engines are composed of narrow passages surrounding the thrust chambers and ensure the reliable operation of the engine. Critical conditions may also be encountered, since the cooling jackets of cryogenic engines, such as those using LOX/LCH4 propellants, are based on a regenerative strategy, where the fuel is used as a refrigerant. Consequently, deterioration modes near where pseudocritical conditions are reached or low heat transfer coefficients where the fuel becomes a vapour and must therefore be managed. The verification of the cooling jacket behaviour to consolidate the design solutions in all the extreme points of the operating box represents a very important phase. The present paper discusses the full characterization of the HYPROB (HYdrocarbon PROpulsion test Bench Program) first unit of the final demonstrator, (DEMO-0A), by considering the working points within the limits of the operating box and comparisons with the nominal conditions are given. In this way, a full understanding of the cooling system behaviour, affecting the working of the entire thrust chamber, is accomplished. Moreover, the design strategy and choices have been confirmed, since the verifications also include potentially even more extreme conditions with respect to the nominal ones. The investigation has been numerically performed and supported the thermo-structural analyses accomplished before the final firing campaign, completed in December 2022. Since little information is available in the literature on LOX/LCH4 engines, suggestions are given as to the organization of the numerical simulations, which support the design of such rocket engine cooling systems.

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1D Numerical Simulations Aimed to Reproduce the Operative Conditions of a $$LOX/LCH_{4}$$ Engine Demonstrator

Romano,

Ricci,

Battista

2024

Aerotec. Missili Spaz.

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Development of a Liquid Rocket Ground Demonstrator Through Thermal Analyses

Cited by 5 publications

References 9 publications

Transcritical Behavior of Methane in the Cooling Jacket of a Liquid-Oxygen/Liquid-Methane Rocket-Engine Demonstrator

Transcritical Behavior of Methane in the Cooling Jacket of a Liquid-Oxygen/Liquid-Methane Rocket-Engine Demonstrator

Thermal Behaviour of the Cooling Jacket Belonging to a Liquid Oxygen/Liquid Methane Rocket Engine Demonstrator in the Operation Box

1D Numerical Simulations Aimed to Reproduce the Operative Conditions of a $$LOX/LCH_{4}$$ Engine Demonstrator

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